About: Application of X-FEM techniques for fatigue crack growth prediction in 3D part of aircraft structure     Goto   Sponge   NotDistinct   Permalink

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Description
  • This article presents a fatigue crack growth prediction for the critical primary structure element (PSE) of the lower wing flange plate of a L-410 UVP-E aircraft as the reference structure element. Crack growth analysis is performed using ABAQUS FE code and AFGROW software. The XFEM capability in ABAQUS was used to model the stationary crack and to determine the stress intensity factor. Computational analyses demonstrate the possibility of predicting fatigue crack growth and preventing in-service failure of the part. The results of the computational analyses were compared with test results.
  • This article presents a fatigue crack growth prediction for the critical primary structure element (PSE) of the lower wing flange plate of a L-410 UVP-E aircraft as the reference structure element. Crack growth analysis is performed using ABAQUS FE code and AFGROW software. The XFEM capability in ABAQUS was used to model the stationary crack and to determine the stress intensity factor. Computational analyses demonstrate the possibility of predicting fatigue crack growth and preventing in-service failure of the part. The results of the computational analyses were compared with test results. (en)
Title
  • Application of X-FEM techniques for fatigue crack growth prediction in 3D part of aircraft structure
  • Application of X-FEM techniques for fatigue crack growth prediction in 3D part of aircraft structure (en)
skos:prefLabel
  • Application of X-FEM techniques for fatigue crack growth prediction in 3D part of aircraft structure
  • Application of X-FEM techniques for fatigue crack growth prediction in 3D part of aircraft structure (en)
skos:notation
  • RIV/00010669:_____/13:#0001558!RIV14-MPO-00010669
http://linked.open...avai/predkladatel
http://linked.open...avai/riv/aktivita
http://linked.open...avai/riv/aktivity
  • I
http://linked.open...iv/cisloPeriodika
  • 2/2013
http://linked.open...vai/riv/dodaniDat
http://linked.open...aciTvurceVysledku
http://linked.open.../riv/druhVysledku
http://linked.open...iv/duvernostUdaju
http://linked.open...titaPredkladatele
http://linked.open...dnocenehoVysledku
  • 61837
http://linked.open...ai/riv/idVysledku
  • RIV/00010669:_____/13:#0001558
http://linked.open...riv/jazykVysledku
http://linked.open.../riv/klicovaSlova
  • Extended Finite Element Method; Fatigue; Crack; Damage tolerance (en)
http://linked.open.../riv/klicoveSlovo
http://linked.open...odStatuVydavatele
  • CZ - Česká republika
http://linked.open...ontrolniKodProRIV
  • [10C18E26DA71]
http://linked.open...i/riv/nazevZdroje
  • Czech Aerospace Proceedings / Letecký zpravodaj
http://linked.open...in/vavai/riv/obor
http://linked.open...ichTvurcuVysledku
http://linked.open...cetTvurcuVysledku
http://linked.open...UplatneniVysledku
http://linked.open...v/svazekPeriodika
  • 2
http://linked.open...iv/tvurceVysledku
  • Doubrava, Radek
issn
  • 1211-877X
number of pages
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